Page 291 - Neural Network Modeling and Identification of Dynamical Systems

282 RESULTS OF COMPUTATIONAL EXPERIMENTS WITH ADAPTIVE SYSTEMS

FIGURE A.56 The results of a computational experiment for the MPC-type control system (mini-UAV X-04), a flight with
airspeed V ind = 70 km/h when fault conditions occur at the time instant t = 10 sec (backwards shift of the center by 10%) and
then at the time instant t = 20 sec (50% decrease in the effectiveness of the longitudinal control). Here α is angle of attack, deg
(dotted line for reference model, solid line for plant); E α is tracking error for the given angle of attack, deg; α ref is reference
signal on the angle of attack, deg; δ e, act is command signal for the elevator actuator, deg; t is time, sec.